GOE 257 AIRFOIL (goe257-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 257 AIRFOIL (goe257-il) Reynolds number: 500,000 Max Cl/Cd: 88.88 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe257-il-500000-n5.txt Download as CSV file: xf-goe257-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 257 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.4255 0.10573 0.10355 -0.0090 1.0000 0.0075
-9.000 -0.4232 0.10140 0.09924 -0.0111 1.0000 0.0077
-8.750 -0.4238 0.09632 0.09418 -0.0136 1.0000 0.0080
-8.500 -0.4196 0.09305 0.09094 -0.0154 1.0000 0.0082
-8.250 -0.4131 0.09054 0.08845 -0.0168 1.0000 0.0084
-8.000 -0.4088 0.08780 0.08573 -0.0183 1.0000 0.0087
-7.750 -0.4028 0.08430 0.08225 -0.0213 0.9951 0.0090
-7.500 -0.3874 0.07925 0.07718 -0.0280 0.9719 0.0092
-7.250 -0.3715 0.07387 0.07176 -0.0348 0.9503 0.0095
-7.000 -0.3567 0.06830 0.06612 -0.0409 0.9271 0.0099
-6.750 -0.3407 0.06073 0.05838 -0.0484 0.9042 0.0105
-6.500 -0.3215 0.05541 0.05288 -0.0530 0.8775 0.0112
-6.250 -0.3016 0.05342 0.05072 -0.0544 0.8385 0.0116
-6.000 -0.2803 0.05028 0.04729 -0.0565 0.7898 0.0123
-5.750 -0.2492 0.03775 0.03410 -0.0638 0.7659 0.0146
-5.500 -0.2251 0.03676 0.03290 -0.0645 0.7420 0.0150
-5.250 -0.2004 0.03603 0.03201 -0.0651 0.7250 0.0155
-5.000 -0.1736 0.03383 0.02958 -0.0662 0.7126 0.0163
-4.750 -0.1396 0.02557 0.02046 -0.0679 0.7048 0.0195
-4.500 -0.1131 0.02469 0.01946 -0.0686 0.6962 0.0200
-4.250 -0.0858 0.02381 0.01844 -0.0691 0.6889 0.0205
-4.000 -0.0576 0.02252 0.01694 -0.0697 0.6827 0.0212
-3.750 -0.0288 0.02116 0.01535 -0.0701 0.6764 0.0223
-3.500 0.0006 0.01962 0.01350 -0.0704 0.6709 0.0235
-3.250 0.0300 0.01829 0.01189 -0.0707 0.6650 0.0240
-3.000 0.0591 0.01728 0.01062 -0.0710 0.6590 0.0245
-2.750 0.0883 0.01677 0.00992 -0.0712 0.6531 0.0251
-2.500 0.1174 0.01612 0.00906 -0.0715 0.6469 0.0257
-2.250 0.1463 0.01497 0.00772 -0.0718 0.6417 0.0260
-2.000 0.1752 0.01399 0.00663 -0.0721 0.6361 0.0265
-1.750 0.2039 0.01337 0.00593 -0.0724 0.6303 0.0269
-1.500 0.2327 0.01289 0.00540 -0.0726 0.6249 0.0274
-1.250 0.2614 0.01248 0.00494 -0.0729 0.6183 0.0278
-1.000 0.2901 0.01213 0.00454 -0.0731 0.6109 0.0281
-0.750 0.3188 0.01182 0.00419 -0.0733 0.6013 0.0284
-0.500 0.3475 0.01158 0.00392 -0.0736 0.5911 0.0291
-0.250 0.3761 0.01136 0.00366 -0.0738 0.5813 0.0297
0.000 0.4049 0.01113 0.00339 -0.0740 0.5715 0.0296
0.250 0.4337 0.01094 0.00316 -0.0743 0.5613 0.0296
0.500 0.4624 0.01080 0.00297 -0.0745 0.5480 0.0296
0.750 0.4911 0.01069 0.00281 -0.0748 0.5334 0.0299
1.000 0.5198 0.01062 0.00269 -0.0750 0.5200 0.0302
1.250 0.5485 0.01058 0.00260 -0.0753 0.5056 0.0308
1.500 0.5769 0.01060 0.00254 -0.0755 0.4881 0.0317
1.750 0.6053 0.01065 0.00251 -0.0757 0.4717 0.0327
2.000 0.6336 0.01071 0.00252 -0.0760 0.4594 0.0335
2.250 0.6619 0.01080 0.00255 -0.0762 0.4464 0.0342
2.500 0.6901 0.01092 0.00259 -0.0764 0.4316 0.0364
2.750 0.7182 0.01103 0.00266 -0.0766 0.4186 0.0402
3.000 0.7464 0.01114 0.00275 -0.0768 0.4080 0.0433
3.250 0.7698 0.00918 0.00291 -0.0765 0.3999 1.0000
3.500 0.7979 0.00935 0.00302 -0.0766 0.3906 1.0000
3.750 0.8261 0.00950 0.00314 -0.0768 0.3798 1.0000
4.000 0.8540 0.00968 0.00329 -0.0770 0.3660 1.0000
4.250 0.8817 0.00992 0.00344 -0.0772 0.3444 1.0000
4.500 0.9088 0.01023 0.00362 -0.0773 0.3104 1.0000
5.000 0.9589 0.01166 0.00444 -0.0773 0.2044 1.0000
5.250 0.9856 0.01202 0.00473 -0.0774 0.1885 1.0000
5.500 1.0120 0.01240 0.00503 -0.0774 0.1667 1.0000
5.750 1.0371 0.01299 0.00542 -0.0774 0.1290 1.0000
6.000 1.0586 0.01418 0.00624 -0.0769 0.0542 1.0000
6.250 1.0840 0.01464 0.00667 -0.0767 0.0406 1.0000
6.500 1.1078 0.01534 0.00723 -0.0764 0.0178 1.0000
6.750 1.1329 0.01582 0.00777 -0.0761 0.0135 1.0000
7.000 1.1580 0.01625 0.00826 -0.0759 0.0123 1.0000
7.250 1.1825 0.01674 0.00883 -0.0756 0.0112 1.0000
7.500 1.2062 0.01732 0.00949 -0.0751 0.0102 1.0000
7.750 1.2283 0.01807 0.01035 -0.0744 0.0092 1.0000
8.000 1.2500 0.01881 0.01118 -0.0737 0.0085 1.0000
8.250 1.2725 0.01940 0.01184 -0.0731 0.0079 1.0000
8.500 1.2935 0.02012 0.01264 -0.0723 0.0074 1.0000
8.750 1.3133 0.02091 0.01351 -0.0713 0.0070 1.0000
9.000 1.3319 0.02176 0.01443 -0.0702 0.0066 1.0000
9.250 1.3486 0.02271 0.01547 -0.0688 0.0063 1.0000
9.500 1.3606 0.02397 0.01683 -0.0668 0.0061 1.0000
9.750 1.3684 0.02543 0.01839 -0.0641 0.0058 1.0000
10.000 1.3791 0.02652 0.01959 -0.0619 0.0057 1.0000
10.250 1.3865 0.02766 0.02084 -0.0591 0.0055 1.0000
10.500 1.3907 0.02893 0.02222 -0.0561 0.0053 1.0000
10.750 1.3951 0.03038 0.02378 -0.0535 0.0051 1.0000
11.000 1.3998 0.03197 0.02549 -0.0513 0.0049 1.0000
11.250 1.4036 0.03377 0.02741 -0.0495 0.0047 1.0000
11.500 1.4065 0.03581 0.02956 -0.0479 0.0046 1.0000
11.750 1.4093 0.03803 0.03189 -0.0467 0.0045 1.0000
12.000 1.4116 0.04043 0.03441 -0.0458 0.0044 1.0000
12.250 1.4133 0.04305 0.03714 -0.0452 0.0043 1.0000
12.500 1.4147 0.04580 0.03999 -0.0448 0.0042 1.0000
12.750 1.4147 0.04877 0.04307 -0.0445 0.0041 1.0000
13.000 1.4134 0.05195 0.04637 -0.0443 0.0040 1.0000
13.250 1.4102 0.05537 0.04990 -0.0441 0.0040 1.0000
13.500 1.4048 0.05910 0.05376 -0.0439 0.0039 1.0000
13.750 1.3965 0.06324 0.05805 -0.0437 0.0038 1.0000
14.000 1.3921 0.06701 0.06198 -0.0439 0.0038 1.0000
14.250 1.3866 0.07104 0.06617 -0.0443 0.0038 1.0000
14.500 1.3803 0.07534 0.07063 -0.0449 0.0037 1.0000
14.750 1.3728 0.07994 0.07540 -0.0458 0.0037 1.0000
15.000 1.3642 0.08487 0.08050 -0.0470 0.0037 1.0000
15.250 1.3548 0.09012 0.08592 -0.0485 0.0036 1.0000
15.500 1.3442 0.09577 0.09175 -0.0503 0.0036 1.0000
15.750 1.3328 0.10172 0.09787 -0.0525 0.0036 1.0000
16.000 1.3204 0.10805 0.10438 -0.0550 0.0036 1.0000
16.250 1.3075 0.11468 0.11118 -0.0579 0.0035 1.0000
16.500 1.2939 0.12169 0.11835 -0.0612 0.0035 1.0000
16.750 1.2799 0.12900 0.12583 -0.0648 0.0035 1.0000
17.000 1.2655 0.13670 0.13369 -0.0690 0.0035 1.0000
17.250 1.2514 0.14471 0.14185 -0.0734 0.0035 1.0000
17.500 1.2370 0.15319 0.15049 -0.0784 0.0035 1.0000
17.750 1.2223 0.16217 0.15961 -0.0838 0.0035 1.0000
18.000 1.2081 0.17138 0.16895 -0.0895 0.0036 1.0000
18.250 1.1935 0.18126 0.17896 -0.0956 0.0036 1.0000
18.500 1.1777 0.19230 0.19012 -0.1024 0.0036 1.0000
18.750 1.1581 0.20612 0.20402 -0.1106 0.0037 1.0000
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